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RU2007119069A - CENTRAL OUTPUT CHANNEL HOUSING OF TURBOREACTIVE ENGINE, TURBOREACTIVE ENGINE - Google Patents

CENTRAL OUTPUT CHANNEL HOUSING OF TURBOREACTIVE ENGINE, TURBOREACTIVE ENGINE Download PDF

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Publication number
RU2007119069A
RU2007119069A RU2007119069/06A RU2007119069A RU2007119069A RU 2007119069 A RU2007119069 A RU 2007119069A RU 2007119069/06 A RU2007119069/06 A RU 2007119069/06A RU 2007119069 A RU2007119069 A RU 2007119069A RU 2007119069 A RU2007119069 A RU 2007119069A
Authority
RU
Russia
Prior art keywords
forming
central
wall
many
clutch
Prior art date
Application number
RU2007119069/06A
Other languages
Russian (ru)
Other versions
RU2451813C2 (en
Inventor
Тома Ален Кристиан ВЕНСАН (FR)
Тома Ален Кристиан ВЕНСАН
Original Assignee
Снекма (Fr)
Снекма
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Снекма (Fr), Снекма filed Critical Снекма (Fr)
Publication of RU2007119069A publication Critical patent/RU2007119069A/en
Application granted granted Critical
Publication of RU2451813C2 publication Critical patent/RU2451813C2/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics
    • F05D2300/6012—Woven fabrics

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

1. Центральный корпус выходного канала продуктов сгорания турбореактивного двигателя, содержащий внешнюю стенку и, по меньшей мере, одну внутреннюю стену, образующие полость между ними, при этом внешняя стенка содержит множество отверстий, выполненных, по меньшей мере, на части входной поверхности для формирования, по меньшей мере, одного резонатора Гельмгольца с полостью, отличающийся тем, что внутренняя стенка содержит гибкую муфту.1. The Central body of the output channel of the combustion products of a turbojet engine containing an outer wall and at least one inner wall forming a cavity between them, while the outer wall contains many holes made at least on part of the input surface for forming, at least one Helmholtz resonator with a cavity, characterized in that the inner wall contains a flexible coupling. 2. Центральный корпус по п.1, отличающийся тем, что внутренняя стенка образована гибкой муфтой.2. The central body according to claim 1, characterized in that the inner wall is formed by a flexible coupling. 3. Центральный корпус по любому из пп.1 или 2, отличающийся тем, что муфта выполнена из текстиля из керамических нитей, предпочтительно на основе кремния или базальта, со сшивной нитью, выполненной, например, на основе кремния или металла.3. The central body according to any one of claims 1 or 2, characterized in that the sleeve is made of textile made from ceramic threads, preferably based on silicon or basalt, with a stitching thread made, for example, based on silicon or metal. 4. Центральный корпус по п.1, отличающийся тем, что муфта выполнена воздухонепроницаемой.4. The Central housing according to claim 1, characterized in that the clutch is airtight. 5. Центральный корпус по п.1, отличающийся тем, что муфта закреплена каждым из своих концов для формирования единой полости, образующей вместе с отверстиями единый резонатор Гельмгольца.5. The Central housing according to claim 1, characterized in that the clutch is fixed by each of its ends to form a single cavity, forming together with the holes a single Helmholtz resonator. 6. Центральный корпус по п.1, отличающийся тем, что содержит множество муфт, формирующих множество полостей, образующих множество резонаторов Гельмгольца.6. The Central building according to claim 1, characterized in that it contains many couplings forming a lot of cavities, forming many Helmholtz resonators. 7. Центральный корпус по п.1, отличающийся тем, что содержит одну муфту с, по меньшей мере, тремя кольцевыми зонами фиксации, формирующими множество полостей, образующих множество резонаторов Гельмгольца.7. The Central housing according to claim 1, characterized in that it contains one clutch with at least three annular zones of fixation, forming many cavities, forming many Helmholtz resonators. 8. Турбореактивный двигатель, содержащий канал выхода первичных газов с центральным корпусом по пп.1-7.8. A turbojet engine containing a primary gas outlet channel with a central casing according to claims 1-7.
RU2007119069/06A 2006-05-23 2007-05-22 Turbojet engine outlet channel central case, and turbojet engine RU2451813C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0604615 2006-05-23
FR0604615A FR2901578B1 (en) 2006-05-23 2006-05-23 CENTRAL BODY FOR EXHAUST CHANNEL OF A TURBOJET, TURBOREACTOR

Publications (2)

Publication Number Publication Date
RU2007119069A true RU2007119069A (en) 2008-11-27
RU2451813C2 RU2451813C2 (en) 2012-05-27

Family

ID=37806841

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2007119069/06A RU2451813C2 (en) 2006-05-23 2007-05-22 Turbojet engine outlet channel central case, and turbojet engine

Country Status (5)

Country Link
US (1) US7886543B2 (en)
EP (1) EP1860313B1 (en)
CA (1) CA2588950C (en)
FR (1) FR2901578B1 (en)
RU (1) RU2451813C2 (en)

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DE102011008921A1 (en) 2011-01-19 2012-07-19 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine exhaust cone
DE102011106959A1 (en) * 2011-07-08 2013-01-10 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine with variable bypass nozzle
US9200537B2 (en) 2011-11-09 2015-12-01 Pratt & Whitney Canada Corp. Gas turbine exhaust case with acoustic panels
US8826669B2 (en) 2011-11-09 2014-09-09 Pratt & Whitney Canada Corp. Gas turbine exhaust case
US8944753B2 (en) 2011-11-09 2015-02-03 Pratt & Whitney Canada Corp. Strut mounting arrangement for gas turbine exhaust case
US9261047B2 (en) 2012-05-29 2016-02-16 Lockheed Martin Corporation Jet exhaust noise reduction
GB201301702D0 (en) 2013-01-31 2013-03-20 Rolls Royce Plc Exhaust cone
US9400108B2 (en) 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
US9488129B1 (en) * 2015-05-13 2016-11-08 King Fahd University Of Petroleum And Minerals Passive edge-tone suppression method
FR3061933B1 (en) * 2017-01-18 2019-08-16 Airbus Operations INTERNAL STRUCTURE OF A PRIMARY EJECTION DUCT
FR3072712B1 (en) * 2017-10-20 2019-09-27 Safran Aircraft Engines TURBOMACHINE REAR PART HAVING AN EFFORTS PATH EXTENDING BETWEEN EJECTION CONE AND EXHAUST CASE INTERNAL VIROLE

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Also Published As

Publication number Publication date
EP1860313B1 (en) 2017-03-22
CA2588950A1 (en) 2007-11-23
US7886543B2 (en) 2011-02-15
FR2901578A1 (en) 2007-11-30
CA2588950C (en) 2014-07-15
US20070272477A1 (en) 2007-11-29
FR2901578B1 (en) 2008-07-25
EP1860313A1 (en) 2007-11-28
RU2451813C2 (en) 2012-05-27

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